Numerical Analysis of Direct and Indirect Noise Produced by a High Pressure Turbine Stage

In response to the continuous increase in aircraft noise pollution, computational aeroacoustic analyses are mandatory during the aero-engine design loop. In order to investigate the acoustic generation and propagation phenomena within a multi-stage turbomachinery, an experimental campaign on direct and indirect noise coming from a high pressure axial turbine stage has been carried out in the context of the European research project RECORD. The purpose of this work is to numerically predict both the direct noise produced by stator/rotor interactions and the indirect noise generated by the non-acoustic fluctuations coming from an annular combustor that impinge on the HPT stage by using URANS analyses. The computational results are in good agreement
with experimental measures, confirming the possibility to include the numerical method during the engine design loop to assess noise emissions and suggest low noise design solutions.